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Degradation in Gas Turbine Systems

[+] Author Affiliations
Rainer Kurz, Klaus Brun

Solar Turbines Incorporated, San Diego, CA

Paper No. 2000-GT-0345, pp. V002T03A003; 10 pages
  • ASME Turbo Expo 2000: Power for Land, Sea, and Air
  • Volume 2: Coal, Biomass and Alternative Fuels; Combustion and Fuels; Oil and Gas Applications; Cycle Innovations
  • Munich, Germany, May 8–11, 2000
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7855-2
  • Copyright © 2000 by ASME


Any prime mover exhibits the effects of wear and tear over time. The problem of predicting the effects of wear and tear on the performance of any engine is still a matter of discussion. Because the function of a gas turbine is the result of the fine tuned cooperation of many different components, the emphasis of this paper is on the gas turbine and its driven equipment (compressor or pump) as a system, rather than on isolated components. We will discuss the effect of degradation on the package as part of a complex system (e.g. a pipeline, a reinjection station, etc.).

Treating the gas turbine package as a system reveals the effects of degradation on the match of the components as well as on the match with the driven equipment. This article will contribute insights into the problem of gas turbine system degradation. Based on some detailed studies on the mechanisms that cause engine degradation, namely

- changes in blade surfaces due to erosion or fouling, and the effect on the blade aerodynamics;

- changes in seal geometries and clearances, and the effect on parasitic flows,

- changes in the combustion system (e.g. which result in different pattern factors),

the effects of degradation will be discussed.

The study includes a methodology to simulate the effects of engine and driven equipment degradation. With a relatively simple set of equations that describe the engine behavior, and a number of linear deviation factors, which can easily be obtained from engine maps or test data, the equipment behavior for various degrees of degradation will be studied. A second model, using a stage by stage model for the engine compressor, is used to model the compressor deterioration. The authors have avoided to present figures about the speed of degradation, because it is subject to a variety of operational and design factors, that typically cannot be controlled entirely.

Copyright © 2000 by ASME
Topics: Gas turbines



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